固体推进剂二维绝热微尺度燃烧模型的数值研究

发布时间：2017-12-27 09:39

本文关键词：固体推进剂二维绝热微尺度燃烧模型的数值研究　出处：《推进技术》2016年12期 　论文类型：期刊论文

【摘要】：为实现固体微推力器工作过程的一体化模拟,基于Fluent计算软件的二次开发功能(UDF)和简化化学动力学模型,实现了固体推进剂的二维气-凝相绝热微尺度燃烧模型的建立,该模型针对固体微推力器所用双基推进剂,包含两步凝相反应和五步气相反应,燃速、推进剂表面温度和组分质量分数基于燃面物理特性计算得到,并考虑了粘性作用对气相和凝相反应的影响。针对0.5MPa,1.0MPa,2.0MPa和5.1MPa四种工况进行了计算,结果表明,高压工作环境下出现发光火焰区,且随表面压力增大而逐渐靠近壁面,凝相反应区厚度和嘶嘶区、暗区主要反应物在燃面的质量分数随推进剂表面压力增大而减小。对称面处推进剂燃速,推进剂表面温度和气相火焰结构与实验结果基本一致。由于壁面附近较高的粘性作用,气相火焰在壁面位置更加靠近推进剂燃面,并导致壁面位置推进剂燃速高于对称面位置。该模型实现了二维环境下考虑分步凝相反应的推进剂绝热燃烧模型的一体化计算,较好地拓展了原模型的应用范围。
[Abstract]:In order to realize the integration of simulation of solid micro thruster working process, two development function based on Fluent (UDF) and simplified chemical kinetic model is established to realize a two-dimensional gas - solid propellant in condensed phase adiabatic micro scale combustion model, the model for solid micro thruster with double base propellant, the condensed phase reaction consists of two steps and the five step gas phase reaction, mass fractions of surface physical properties based on the calculated propellant burning rate, surface temperature and group, and considering the effect of viscosity on the gas phase and the condensed phase reaction. According to 0.5MPa, 1.0MPa, 2.0MPa and 5.1MPa in four different conditions were calculated. The results show that the high pressure working environment under the luminous flame area, and with the surface pressure increases gradually near the wall, the condensed phase reaction zone thickness and hissing area, dark area main reactants in the burning mass fraction decreases with the pressure of the propellant surface increase. The propellant burning rate at the symmetric surface, the surface temperature of the propellant and the flame structure of the gas phase are basically the same as the experimental results. Due to the viscous effect near the wall is high, gas flame in the wall position closer to the propellant, and causing the wall position of the burning rate of the propellant is higher than the plane of symmetry position. The model realizes the integrated calculation of the propellant adiabatic combustion model considering the stepwise condensation reaction under two-dimensional environment, which extends the application scope of the original model.
【作者单位】：北京理工大学宇航学院;北京控制工程研究所;
【分类号】：V512
【正文快照】： 1引言固体微推力器是微小型航天器的姿轨控动力系统,具有结构简单,无可动部件及其带来的摩擦损失等特点,且集成度高,可以集成在基板上以阵列形式实现,实现对微小型航天器的姿态和轨道控制[1~6]。固体微推力器的燃料是固体推进剂。固体推进剂的火焰区呈现了一定的微尺度特征,火

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